Accession Number : ADB018467

Title :   Wind Tunnel Experiments on the Effect of Combustion in the Wake Region of Supersonic Projectiles-Test Series III

Descriptive Note : Memorandum rept.

Corporate Author : ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s) : Ward, J Richard ; Baltakis, Frank P ; Mancinelli, Dennis J

PDF Url : ADB018467

Report Date : Apr 1977

Pagination or Media Count : 61

Abstract : This report summarizes the third set of wind tunnel tests to evaluate the effect of combustion of pyrotechnics on the base drag of supersonic projectiles. In this test series, a larger diameter model was used to expand the range of injection parameters for R20C. It was found that the base pressure rise vs I, the injection parameter, for R20C could be correlated by an expression requiring two parameters. The maximum base drag reduction achieved with pyrotechnics at M sub infinity = 2.0 was 68%. The maximum specific impulse at M sub infinity = 2.0 was nearly 8kN-s/kg. The maximum specific impulse was observed at an I value of 0.002. Direct measurement of the specific impulse by means of a force balance agreed with the specific impulses computed from integrating base pressure-time histories.

Descriptors :   *AERODYNAMIC DRAG, *TRACER AMMUNITION, BASE FLOW, BLEED SYSTEMS, COMBUSTION, COMBUSTION STABILITY, IMPULSE LOADING, PRESSURE DISTRIBUTION, PYROTECHNICS, RANGE(DISTANCE), SUPERSONIC CHARACTERISTICS, WAKE, WIND TUNNEL TESTS

Subject Categories : Pyrotechnics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE